US20140345199A1 - Gasket seal, door of aircraft, seal structure for opening portion of aircraft, and aircraft - Google Patents
Gasket seal, door of aircraft, seal structure for opening portion of aircraft, and aircraft Download PDFInfo
- Publication number
- US20140345199A1 US20140345199A1 US14/345,460 US201214345460A US2014345199A1 US 20140345199 A1 US20140345199 A1 US 20140345199A1 US 201214345460 A US201214345460 A US 201214345460A US 2014345199 A1 US2014345199 A1 US 2014345199A1
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- US
- United States
- Prior art keywords
- opening portion
- gasket seal
- seal
- aircraft
- door
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/064—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces the packing combining the sealing function with other functions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
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- E—FIXED CONSTRUCTIONS
- E06—DOORS, WINDOWS, SHUTTERS, OR ROLLER BLINDS IN GENERAL; LADDERS
- E06B—FIXED OR MOVABLE CLOSURES FOR OPENINGS IN BUILDINGS, VEHICLES, FENCES OR LIKE ENCLOSURES IN GENERAL, e.g. DOORS, WINDOWS, BLINDS, GATES
- E06B7/00—Special arrangements or measures in connection with doors or windows
- E06B7/16—Sealing arrangements on wings or parts co-operating with the wings
- E06B7/22—Sealing arrangements on wings or parts co-operating with the wings by means of elastic edgings, e.g. elastic rubber tubes; by means of resilient edgings, e.g. felt or plush strips, resilient metal strips
- E06B7/23—Plastic, sponge rubber, or like strips or tubes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/021—Sealings between relatively-stationary surfaces with elastic packing
- F16J15/022—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material
- F16J15/024—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/021—Sealings between relatively-stationary surfaces with elastic packing
- F16J15/022—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material
- F16J15/024—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity
- F16J15/027—Sealings between relatively-stationary surfaces with elastic packing characterised by structure or material the packing being locally weakened in order to increase elasticity and with a hollow profile
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Gasket Seals (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
To reliably prevent entrance of electro-magnetic waves in a door that closes an opening portion formed in an airframe of an aircraft. A gasket seal 20 which is arranged between an opening portion 12 formed in an airframe of an aircraft and a door 13 for closing the opening portion 12, includes: a gasket seal body that is made of a rubber material; and conductive fiber 24 that covers a surface of the gasket seal body. When the door 13 is in a closed state, the gasket seal 20 whose surface is made conductive is abutted against a striker 30 provided on a skin 11 side of the airframe and made of a conductive material. The door 13 and the skin 11 of the airframe are electrically connected together via the conductive fiber 24 and the striker 30, and electro-magnetic waves can be reliably shielded.
Description
- The present invention relates to a gasket seal, a door of an aircraft, and a seal structure for an opening portion of an aircraft. The present invention also relates to an aircraft having the seal structure.
- Aircrafts must be able to fly safely with no malfunction or unexpected behavior caused during a cruising flight or during landing and takeoff under high intensity radiated fields (HIRF) as an electro-magnetic environment from radios, televisions, radars, transmitters, and other sources. Therefore, HIRF protection measures required in (14CFR) §§23.1308, 25.1317, 27.1317, and 29.1317, High-intensity Radiated Fields (HIRF) protection, which stipulate Regulations (airworthiness requirements) of FAA (Federal Aviation Administration) need to be taken.
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FIG. 7 is a view for explaining an HIRF environment when an aircraft approaches an air control radar antenna of an airport during landing or takeoff. In this case, intensive radiated fields are determined based on a slant range to the antenna and a look angle from the antenna. - Recently, the importance of protection of electric/electronic systems of aircrafts has been significantly increasing because of the following reasons:
- 1) a greater dependence on electric/electronic systems that execute required functions for continued safe flight and landing of aircrafts;
2) a decrease in electro-magnetic shielding by a certain type of composite material used in design of aircrafts;
3) an increase in susceptibility (sensitivity) of electric/electronic systems to HIRF along with increases in operating speed of data buses or processors, density of ICs or cards, and sensitivity of electronics;
4) an expansion of a usage frequency particularly to a high-frequency band of 1 GHz or more;
5) an increase in severity of an HIRF environment along with an increase in the number of RF transmitters and electric power; and
6) an adverse effect on part of aircrafts when exposed to HIRF. - Meanwhile, inside aircrafts, there may be an adverse effect on, for example, communications with an airport control tower, and communications or control of navigation for a flight along a predetermined route due to radio waves or electro-magnetic noise (simply referred to as electro-magnetic noise below) from various electronics such as mobiles, game machines, and notebook computers, or PEDs (Personal Electro Devices) such as active-type RFID (Radio Frequency IDentification) tags attached to air cargos. Thus, as is well known, passengers are asked to refrain from using various electronics inside aircrafts.
- Airframes of aircrafts are generally formed of a metal material, and electro-magnetic noise is thus attenuated. Thus, the electro-magnetic noise enters and exits mainly through windows of a cabin and a cockpit. To prevent the electro-magnetic noise that possibly causes a failure from entering the cockpit or an avionics bay from windows, a film of ITO (Indium Tin Oxide), gold, silver or the like is provided so as to be inserted into a window obtained by laminating a plurality of window panels made of acrylic or the like (e.g., see Patent Literature 1).
- Meanwhile, as shown in
FIG. 8 , various opening portions are formed in an airframe of an aircraft in order to allow boarding, inspection, or the like. Doors for closing the opening portions are generally formed of a metal material of the same type as the airframe. - A gasket seal made of an insulating rubber material is provided on one of the door and the opening portion on the airframe side so as to maintain airtightness and prevent intrusion of water (e.g., see
Patent Literatures 2 to 5). Anticorrosion treatment is applied to the other side which the gasket seal contacts by anodizing and coating. -
- Patent Literature 1:
- National Publication of International Patent Application, Publication No. JP2003-523911
- Patent Literature 2:
- U.S. Pat. No. 3,802,125
- Patent Literature 3:
- U.S. Pat. No. 4,312,153
- Patent Literature 4:
- U.S. Pat. No. 4,854,010
- Patent Literature 5:
- U.S. Patent Application Publication No. 2008/0164373
- Since the door and the airframe of the aircraft are made of a conductive material such as metal, electro-magnetic waves can be prevented from entering from outside. On the other hand, the gasket seal made of a rubber material is arranged in a gap between the opening portion formed in the airframe of the aircraft and the door. The gasket seal is normally fabricated from EPDM rubber (ethylene-propylene-diene rubber) or silicone rubber for the purpose of achieving airtight sealing properties so as to maintain an atmospheric pressure within the airframe against a low pressure outside the airframe, and so as to prevent rain or moisture from entering from outside.
- However, since the gasket seal is made of a non-conductive material, the gasket seal does not have an electro-magnetic shielding effect. Thus, electro-magnetic waves pass through the gasket seal directly without being attenuated in a high frequency band with a half wavelength (½ wavelength) or less by allowing the gasket seal to act like an opening slot (an entrance for radio waves). Therefore, the electro-magnetic waves enter the airframe from the gasket seal to possibly affect electronics mounted inside the airframe.
- The present invention has been accomplished in view of the technical problem as described above, and an object thereof is to provide a seal structure or the like for an opening portion of an aircraft which can reliably prevent entrance of electro-magnetic waves.
- To achieve the above object, the present invention provides a novel gasket seal having conductivity. That is, the present invention provides a gasket seal which is arranged between an opening portion formed in an airframe of an aircraft and a closing body for closing the opening portion, the gasket seal including: a gasket seal body that is made of a rubber material; and conductive fiber that covers a surface of the gasket seal body. Here, examples of the closing body for closing the opening portion include a door and an escape hatch. The surface of the gasket seal is made conductive by using the conductive fiber, so that entrance of electro-magnetic waves from the gasket seal can be prevented without deteriorating airtight sealing performance of the gasket seal.
- As the conductive fiber, one of a) synthetic fiber where a metal plating film is formed on a surface, b) metal fiber, and c) polymer fiber including a conductive material may be used.
- The present invention also provides a seal structure for an opening portion of an aircraft using the above gasket seal. The seal structure includes: the closing body that closes the opening portion formed in the airframe of the aircraft; the gasket seal provided on one of the opening portion and the closing body; and a metallic fitting that is provided on the other of the opening portion and the closing body, and electrically connected to the gasket seal. The opening portion of the aircraft and the closing body that closes the opening portion are electrically connected together via the gasket seal whose surface is made conductive, and the metallic fitting. Accordingly, a return path for lightning current and a bonding path (grounding path) for static electricity can be configured in an airframe structure while preventing the entrance of electro-magnetic waves from the gasket seal. Examples of the metallic fitting include a striker, a scuff plate, and a bonding strap.
- A base material of the striker and the scuff plate is a conductive material, and when the closing body is closed, the striker or the scuff plate is abutted against the gasket seal. The striker or the scuff plate preferably includes a plating layer at least on a contact surface with the conductive fiber of the gasket seal. By appropriately selecting a metal material constituting the conductive fiber and a metal material constituting the above plating layer, galvanic corrosion due to joining of dissimilar metals defined in MIL-STD-889 can be prevented even under moisture and salt spray environments. To be more specific, it is preferable that the metal material constituting the plating layer and the metal material constituting the conductive fiber have the same or almost the same anodic index in view of preventing the above galvanic corrosion. When the anodic indexes of the two metal materials are not equal to each other but a difference between the anodic indexes is an absolute value of 0.15 V or less, “the anodic indexes are almost equal to each other” in the present specification.
- To prevent corrosion of aluminum alloy constituting the airframe due to galvanic corrosion, aluminum alloy may be changed to corrosion resistant steel (CRES). However, it is more disadvantageous to use a large amount of corrosion resistant steel in the aircraft since the weight of the aircraft is increased.
- On the other hand, in accordance with the method of the present invention in which the material of the conductive fiber of the gasket seal and the material of the plating layer of the striker or the scuff plate are appropriately selected, galvanic corrosion can be easily and inexpensively prevented from occurring while reducing the weight, that is, without an increase in the weight of the airframe.
- The present invention may also provide an aircraft having the above seal structure.
- In accordance with the present invention, the entrance of electro-magnetic waves from the gasket seal can be prevented without deteriorating the airtight sealing performance of the gasket seal.
- Also, in accordance with the present invention, the door and the airframe side can be electrically connected together via the gasket seal whose surface is made conductive, and the metallic fitting such as the striker. Because of the electro-magnetic shielding structure, a gap between the closing body (the door, the hatch or the like) and a door frame on the opening portion side of the airframe can be electrically closed, and radio waves or electro-magnetic noise can be prevented from entering from an electro-magnetic gap.
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FIG. 1 is a sectional view illustrating one example of a seal structure for an opening portion of an aircraft according to a first embodiment. -
FIGS. 2A and 2B are sectional views illustrating modifications of the first embodiment. -
FIG. 3 is a sectional view illustrating a seal structure for an opening portion of an aircraft according to a second embodiment. -
FIG. 4A is a sectional view illustrating a seal structure for an opening portion of an aircraft according to a third embodiment; andFIG. 4B is an enlarged view of a gasket seal according to the third embodiment. -
FIG. 5 is a graph illustrating an electro-magnetic shielding measurement result (vertical polarization) when the gasket seal according to the third embodiment is used. -
FIG. 6 is a graph illustrating an electro-magnetic shielding measurement result (horizontal polarization) when the gasket seal according to the third embodiment is used. -
FIG. 7 is a view illustrating an HIRF (High Intensity Radiated Fields) environment that an aircraft encounters. -
FIG. 8 is a view illustrating doors and hatches of an aircraft. - In the following, the present invention is described in detail based on embodiments shown in the accompanying drawings.
- As shown in
FIG. 1 , an openingportion 12 is formed in askin 11 of an airframe of anaircraft 10 in order to allow boarding, inspection or the like, and adoor 13 is openably provided in the openingportion 12. - Here, the
skin 11 and thedoor 13 are formed of a conductive material such as aluminum alloy. - A
gasket seal 20 is fixed to one of thedoor 13 and the openingportion 12, and astriker 30 whose distal end is abutted against thegasket seal 20 is provided on the other of thedoor 13 and the openingportion 12. - Although the
gasket seal 20 is provided on thedoor 13, and thestriker 30 is provided on the openingportion 12 side in the present embodiment, the present invention is of course not limited thereto. That is, thegasket seal 20 may be provided on the openingportion 12 side, and thestriker 30 may be provided on thedoor 13. - The
gasket seal 20 is made of a rubber material having elasticity, and can be fabricated by, for example, molding. Examples of the rubber material include silicone rubber, and EPDM rubber (ethylene-propylene-diene rubber). The rubber material in the present application widely includes elastomer and rubber. - The
gasket seal 20 comprises aseal portion 21, and abase portion 22 that is formed integrally with theseal portion 21 at one end thereof. Theseal portion 21 is provided in an annular shape continuously along an outer peripheral portion of thedoor 13, and has ahollow portion 21 a therein in sectional view. Thebase portion 22 has a rectangular section, and is provided continuously along the outer peripheral portion of thedoor 13. - The
hollow portion 21 a may be formed as an air layer that maintains one atmosphere. - The
gasket seal 20 does not always need to have thehollow portion 21 a composed of the air layer. For example, silicone sponge or the like may be arranged in thehollow portion 21 a to provide a gasket seal with no air layer therein. - Although the
gasket seal 20 having a P-shaped sectional shape as a whole is shown inFIG. 1 , this is merely one example. The sectional shape of thegasket seal 20 is not limited to the P shape, and may be a D shape, or deformed shapes thereof. - The
gasket seal 20 is retained on thedoor 13 with thebase portion 22 fitted to aseal retention portion 14. Theseal retention portion 14 is formed on aback surface 13 a of thedoor 13 that is directed to the inner side of the aircraft. Theseal retention portion 14 is formed of a conductive material such as aluminum alloy similarly to thedoor 13. - An
edge member 31 that projects to the inner side of the aircraft is formed along a peripheral edge portion of the openingportion 12 on theskin 11 side of the airframe. Thestriker 30 is attached to theedge member 31. That is, theedge member 31 functions as a door frame. Oneend portion 30 a of thestriker 30 is joined to theedge member 31 by a joint member such as a rivet having conductivity. Theother end portion 30 b of thestriker 30 is provided so as to be located inward of the openingportion 12, facing theseal portion 21 of thegasket seal 20 attached to thedoor 13. - When the
door 13 is closed, adistal end portion 30 c of thestriker 30 is abutted against theseal portion 21 of thegasket seal 20 to compress and deform theseal portion 21 in a crushing direction. Sealing properties of the openingportion 12 formed in the airframe are thereby ensured. - The
striker 30 is normally made of a conductive material such as aluminum alloy as a base material. - A first feature of the present invention is that a surface of the
gasket seal 20 is covered withconductive fiber 24. When thegasket seal 20 made of a rubber material is covered with theconductive fiber 24, the surface of thegasket seal 20 can be made conductive. Accordingly, electro-magnetic waves can be prevented from entering the airframe from thegasket seal 20 between thedoor 13 and the airframe. - Here, the gasket seal may be also made conductive by mixing a conductive filler such as metal into a rubber material without using the
conductive fiber 24. However, in this method, when the conductive filler in an amount sufficient enough to prevent the entrance of electro-magnetic waves is mixed into the rubber material, flexibility, stretch, resilience, hardness or the like of the gasket seal are affected, so that airtight sealing performance of the gasket seal is deteriorated. Meanwhile, in accordance with the method of the present invention in which the surface of thegasket seal 20 is made conductive by covering the surface of thegasket seal 20 with theconductive fiber 24, the entrance of electro-magnetic waves from thegasket seal 20 can be prevented without deteriorating the airtight sealing performance of thegasket seal 20. - A gap between the
door 13 and the openingportion 12 of the airframe may be also electro-magnetically shielded by a metallic gasket having spring characteristics. Examples of the metallic gasket include a commercially-available Finger Stock fabricated from metal such as beryllium copper and corrosion resistant steel (CRES). However, since the metallic gasket has a gap and does not have airtight sealing performance, thegasket seal 20 made of a rubber material is used in the present invention as described above. - As one example of the
conductive fiber 24, synthetic fiber where a metal plating film is formed on a surface is cited. When thedoor 13 is made of aluminum alloy, an electro-magnetic shielding effect can be obtained by using a good conductor such as Ag, Cu, Ni, Tin, Cr, and Au as a material of the above metal plating. - As another example of the conductive fiber, (i) metal fiber, and (ii) polymer fiber including a conductive material such as metal, or a compound thereof, or carbon black having conductivity are cited.
- The electro-magnetic shielding effect can be also obtained by using, for example, metal fiber made of the above good conductor, or polymer fiber including a filler of the above good conductor or carbon black.
- In the aforementioned configuration, the
gasket seal 20 covered with theconductive fiber 24 is provided along the outer periphery of thedoor 13, and electrically grounded to the openingportion 12 of the airframe via thestriker 30. Accordingly, a shielding structure made of a conductive material can be formed in the gap portion between thedoor 13 and the openingportion 12 of the airframe with no electric gap therebetween, so that the entrance of electro-magnetic noise into the airframe can be prevented. - As described above, the
conductive gasket seal 20 for preventing the entrance of electro-magnetic noise can be reliably, easily, and inexpensively electrically grounded to the openingportion 12 of the airframe. - Also, when the
door 13 is struck by lightning, a return path for lightning current can be configured in the airframe structure by theseal retention portion 14 on thedoor 13 side, theconductive fiber 24, and thestriker 30 provided at the openingportion 12 of the airframe. Also, when thedoor 13 is charged with static electricity (P-Static: Precipitation Static) generated by friction with hail, rain, snow, and dust during a flight, an electricity-removing bonding path (grounding path) for static electricity can be similarly configured in the airframe structure by theseal retention portion 14 on thedoor 13 side, theconductive fiber 24, and thestriker 30 provided at the openingportion 12 of the airframe. - A second feature of the present invention is that the
striker 30 includes aplating layer 32 at least on a surface of thedistal end portion 30 c (i.e., a contact surface with theconductive fiber 24 that covers the surface of the gasket seal 20). - As described above, the base material of the
striker 30 is normally aluminum alloy. Although corrosion of aluminum alloy may be prevented not only by electrolytic treatment, but also by chemical conversion treatment (surface treatment for chemically forming an oxide film on a surface of aluminum alloy; examples thereof include boehmite process, MBV (Modifizierte Bauer Vogel) process, phosphate process, and chromate process), the chemical conversion treatment (an oxide film) is not suitable since the chemical conversion treatment cannot ensure conductivity. Thus, in the present invention, theplating layer 32 is formed at least on the surface of thedistal end portion 30 c of thestriker 30. - A nickel plating layer or a chrome plating layer is preferably used as the
plating layer 32. Particularly, when theplating layer 32 is formed by hard chrome plating or electroless nickel plating, mechanical characteristics such as abrasion resistance and vibration resistance of thestriker 30 can be also improved. Therefore, the hard chrome plating and the electroless nickel plating are preferably used for theplating layer 32 of thestriker 30 that is abutted against thegasket seal 20 every time thedoor 13 is closed. - Since hardness of an electroless nickel film can be increased by heat treatment, abrasion resistance can be also improved. The electroless nickel film is also provided with representative characteristics of a plating film, and has excellent throwing power and chemical resistance, and high decorativeness. Color may be also changed by plating gold or chrome on the electroless nickel film.
- The
plating layer 32 may be also formed by tin plating, silver plating, and zinc plating. The aluminum alloy material may be also plated by the above materials, and tin plating, silver plating, and zinc plating films are also provided with the representative characteristics of the plating film. - The
plating layer 32 may be formed so as to cover at least an entire region of a contact portion between thegasket seal 20 and thestriker 30. - An insulating coating layer (an anticorrosion coating) 33 that prevents corrosion of the
striker 30 itself may be further formed on a portion of thestriker 30 other than the portion where theplating layer 32 is formed. Thecoating layer 33 is formed so as to coverend portions plating layer 32, and theplating layer 32 and thecoating layer 33 cover theentire striker 30. As shown inFIG. 1 , theend portions plating layer 32 are located on an opposite side from thedistal end portion 30 c of thestriker 30 abutted against thegasket seal 20. - By providing the
coating layer 33, corrosion (galvanic corrosion) in a boundary portion between theplating layer 32 and the base material of thestriker 30, or another portion can be prevented. Accordingly, it is not necessary to use a CRES material as the base material of thestriker 30 so as to prevent corrosion, and it is possible to use aluminum alloy, so that thestriker 30 can be formed while an increase in weight is suppressed. - In the above configuration, the
gasket seal 20 is provided on theback surface 13 a of thedoor 13, and the surface of thegasket seal 20 is covered with theconductive fiber 24. When thedoor 13 is in a closed state, thegasket seal 20 covered with theconductive fiber 24 is abutted against thestriker 30 that is provided on theskin 11 side of the airframe, and the base material and theplating layer 32 of which are made of a conductive material. Accordingly, while not only ensuring airtightness and water proof properties between thedoor 13 and the openingportion 12 of the airframe, electro-magnetic waves can be also reliably shielded since thedoor 13 and theskin 11 of the airframe are electrically connected together via theconductive fiber 24, and theplating layer 32 and the base material of thestriker 30. - Here, examples of a preferable combination between the
plating layer 32 of thestriker 30 and theconductive fiber 24 that covers the surface of thegasket seal 20 are described. When the following combinations are employed, corrosion of theconductive fiber 24 or thestriker 30 due to galvanic corrosion between dissimilar metals can be prevented. - —Case 1: When the
Plating Layer 32 of theStriker 30 is a Nickel Plating Layer.— - In the
case 1, conductive fiber obtained by forming a metal plating film containing nickel, copper, silver, gold, or alloy thereof as a main component on a surface of synthetic fiber such as polyester fiber and polyurethane fiber is preferable as theconductive fiber 24. - —Case 2: When the
Plating Layer 32 of theStriker 30 is a Chrome Plating Layer or a Tin Plating Layer.— - In the
case 2, theconductive fiber 24 can be formed by metal fiber formed of 300 series stainless steel, 400 series stainless steel, or 2000 series aluminum alloy. - Although the configuration in which the
gasket seal 20 itself is formed of non-conductive silicone rubber, EPDM rubber or the like, and the surface of thegasket seal 20 is covered with theconductive fiber 24 is described above, a body of thegasket seal 20 itself may have conductivity. - That is, the body of the
gasket seal 20 itself may be formed of conductive EPDM rubber, conductive silicone rubber, conductive silicone elastomer or the like obtained by causing a rubber material such as EPDM rubber and silicone rubber to contain a metallic filler of Ag, Cu, Ni, Al and the like, or carbon particles. Instead of the above metallic filler, Ag/Cu, Ag/Al, Ni/Cu, Ni/Al, Ag/C, Ni/C and the like may be used. - Even when the body of the
gasket seal 20 is formed of a conductive rubber material, the surface of the body of thegasket seal 20 is covered with theconductive fiber 24. Since the conductive rubber material and theconductive fiber 24 are used, the electro-magnetic shielding effect of thegasket seal 20 can be improved. - In the present specification, terms such as “Ag/Cu” have the following meanings.
- Ag/Cu: a filler in which outer surfaces of copper particles are silver-plated.
- Ag/Al: a filler in which outer surfaces of aluminum particles are silver-plated.
- Ni/Cu: a filler in which outer surfaces of copper particles are nickel-plated.
- Ni/Al: a filler in which outer surfaces of aluminum particles are nickel-plated.
- Ag/C: a filler in which outer surfaces of graphite carbon particles are silver-plated.
- Ni/C: a filler in which outer surfaces of graphite carbon particles are nickel-plated.
- Although the gap between the
door 13 and the openingportion 12 is closed by thegasket seal 20 and thestriker 30 having a sectional shape as shown inFIG. 1 in the above embodiment, the present invention is not limited thereto. - For example, although the
distal end portion 30 c of thestriker 30 is abutted against the distal end surface of theseal portion 21 of thegasket seal 20 in a perpendicular direction inFIG. 1 , adistal end portion 30C of astriker 30A may be abutted against the distal end surface of theseal portion 21 of agasket seal 20A in parallel therewith as shown inFIG. 2A . - Moreover, as shown in
FIG. 2B , theseal portion 21 of a gasket seal 20B may be formed in a flat-plate shape extending in a belt-like shape from thebase portion 22. Furthermore, aflat portion 30 d of astriker 30B may contact theseal portion 21. - A second embodiment shows an example in which a gasket seal 20C is abutted against a
scuff plate 50 that is arranged around adoor frame 100. Elements common to those in the aforementioned configuration are assigned the same reference numerals, and description thereof is omitted. - As show in
FIG. 3 , the gasket seal 20C comprises theseal portion 21 and abase portion 22A that is formed integrally with theseal portion 21 at one end thereof. The gasket seal 20C is fixed along the outer periphery of thedoor 13 with theentire base portion 22A and a portion of theseal portion 21 fitted to aseal retention portion 14A. Theseal retention portion 14A includes an outer-sideseal retention portion 14 a that is arranged on an outer peripheral edge portion of thedoor 13, and an inner-sideseal retention portion 14 b that is arranged on an inner side of thedoor 13 relative to the outer-sideseal retention portion 14 a. The outer-sideseal retention portion 14 a is fixed by a fixing rivet R, and the inner-sideseal retention portion 14 b is fixed by a fixing fastener F to thedoor 13, respectively. - Although the surface of the gasket seal 20C is covered with the aforementioned
conductive fiber 24, theconductive fiber 24 is omitted inFIG. 3 . Thescuff plate 50 is formed of a conductive material such as aluminum alloy. - When the
door 13 is in a closed state, the gasket seal 20C is electrically connected to thescuff plate 50 that is arranged around thedoor frame 100 and is made of a conductive material. That is, the gasket seal 20C is electrically grounded to thedoor frame 100 via thescuff plate 50. In accordance with the configuration, the electro-magnetic shielding structure is achieved between thedoor 13 and thedoor frame 100. - A
plating layer 32A may be formed on thescuff plate 50 in a similar manner to the first embodiment in which theplating layer 32 is formed on thestriker 30. Theplating layer 32A is preferably formed so as to cover at least a contact portion between thescuff plate 50 and theconductive fiber 24. A preferable combination between theplating layer 32A and theconductive fiber 24 is as described above. For example, when theconductive fiber 24 of the gasket seal 20C is synthetic fiber where a metal plating film is formed on a surface, theplating layer 32A is preferably formed on thescuff plate 50 such that an anodic index of a metal material constituting theplating layer 32A of thescuff plate 50 is equal to or almost equal to an anodic index of a metal material constituting the metal plating film of theconductive fiber 24. Also, when theconductive fiber 24 of the gasket seal 20C is metal fiber, theplating layer 32A is preferably formed on thescuff plate 50 such that an anodic index of a metal material constituting the metal fiber is equal to or almost equal to the anodic index of the metal material constituting theplating layer 32A of thescuff plate 50. - A third embodiment shows an example in which a
gasket seal 20D is provided on thedoor 13 side via a door-side bonding strap (a first bonding strap) 60A. - As shown in
FIGS. 4A and 4B , thegasket seal 20D comprises theseal portion 21, and abase portion 22B that is formed integrally with theseal portion 21 at one end thereof. Thegasket seal 20D has a P shape in sectional view, and the surface thereof is covered with the aforementionedconductive fiber 24. Theconductive fiber 24 is omitted inFIGS. 4A and 4B . - The door-
side bonding strap 60A has a substantially L shape in sectional view. Thegasket seal 20D is fixed to thedoor 13 via a bolt B and a nut N while thebase portion 22B of thegasket seal 20D is held between a washer W and the door-side bonding strap 60A. - The bolt B penetrates the
base portion 22B of thegasket seal 20D. Therefore, thebase portion 22B is reinforced so as to have higher rigidity than the seal portion 21A by inserting a core formed of glass fiber or the like into thebase portion 22B. - One end of the door-
side bonding strap 60A is abutted against one end of an airframe opening portion-side bonding strap (a second bonding strap) 60B when thedoor 13 is closed. One end of the airframe opening portion-side bonding strap 60B is fixed to the edge member (the door frame) 31 provided at the airframe opening portion with a fixture such as a bolt and a nut. The door-side bonding strap 60A and the airframe opening portion-side bonding strap 60B are metallic fittings fabricated from corrosion resistant steel (CRES) or the like. - In the third embodiment, the
gasket seal 20D whose surface is covered with theconductive fiber 24 is also arranged between thedoor 13 and the openingportion 12 of theairframe 11. Accordingly, electro-magnetic waves from outside of the airframe can be prevented from entering the airframe through thegasket seal 20D. Thegasket seal 20D is also electrically grounded to thedoor 13 via the door-side bonding strap 60A that supports thegasket seal 20D. When thedoor 13 is closed, the door-side bonding strap 60A is abutted against the airframe opening portion-side bonding strap 60B. In accordance with the configuration, the electro-magnetic shielding structure is achieved between thedoor 13 and the openingportion 12 of theairframe 11. - For charging with lightning return current when the
door 13 is struck by lightning, and static electricity (P-static) during a flight, electricity can be reliably passed to the airframe structure from the bonding straps 60A and 60B so as to remove static electricity. - Also, galvanic corrosion due to joining of dissimilar metals under moisture and salt spray environments is designed so as not to occur among the
gasket seal 20D, the door-side bonding strap 60A, and the airframe opening portion-side bonding strap 60B. - For example, conductive fiber obtained by forming a metal plating film containing nickel (with an anodic index of 0.30), copper (with an anodic index of 0.35), or nickel copper alloy (with an anodic index of 0.30) as a main component on a surface of synthetic fiber such as polyester fiber and polyurethane fiber is used as the
conductive fiber 24 that covers the surface of thegasket seal 20D. The bonding straps 60A and 60B are formed of the same type of corrosion resistant steel (CRES; with an anodic index of 0.35), and a plating layer containing nickel (with an anodic index of 0.30) or nickel chrome alloy (with an anodic index of 0.35) as a main component is formed on a contact portion of thebonding strap 60A with theconductive fiber 24. As described above, the bonding straps 60A and 60B are formed of the same type of corrosion resistant steel, and such materials are selected that an anodic index of a metal material constituting the metal plating film of theconductive fiber 24 is equal to or almost equal to an anodic index of a metal material constituting the plating layer of thebonding strap 60A, so that the occurrence of galvanic corrosion can be prevented. - An electro-magnetic shielding test was performed by using the
gasket seal 20D described in the third embodiment based on IEEE STD-299-2006 “IEEE Standard Method for Measuring the Effectiveness of Electromagnetic Shielding Enclosures”. An electro-magnetic shielding effect obtained when the number of the bonding straps 60 for electrically connecting thegasket seal 20D was set to 10 is shown inFIGS. 5 and 6 . The body of thegasket seal 20D was made of silicone rubber, and did not include a conductive filler therein. Nickel-plated polyester fiber was used as theconductive fiber 24 covering the surface of thegasket seal 20D. Theconductive fiber 24 was attached to the surface of thegasket seal 20D by conductive silicone rubber. - As shown in
FIGS. 5 and 6 , the electro-magnetic shielding effect within a frequency band of 100 MHz to 18 GHz was 30 dB or more by using thegasket seal 20D whose surface was covered with theconductive fiber 24. - Although the example in which the gasket seal 20 (20A to 20D) is applied to the
door 13 or the openingportion 12 of the airframe of theaircraft 10 is described in the above embodiments, the application of thegasket seal 20 is not limited to thedoor 13, but it can be of course applied to an escape hatch or the like shown inFIG. 8 . This is because the escape hatch is also attached to the openingportion 12 formed in theskin 11 constituting the airframe of theaircraft 10, and it is necessary to arrange an airtight gasket seal between the openingportion 12 and the escape hatch. Examples of thedoor 13 include an openable entry door, a service door, a cargo door, and an avionics bay door of theaircraft 10 as shown inFIG. 8 . - The present invention may also relate to an aircraft having the electro-magnetic shielding structure as described above. The present invention may be also applied to a case in which a gasket seal at an opening portion such as a maintenance/inspection panel, and a manhole of the aircraft is made conductive. The manhole is a cavity provided so as to allow inspection and maintenance of an inner portion of a wing as a fuel tank.
- Moreover, the gasket seal of the present invention may be applied as a pressure seal for a vent door provided in the entry door or the like.
- Although the example in which the gasket seal 20 (20A to 20D) is applied to one of the opening
portion 12 formed in theskin 11 and thedoor 13 is described, the gasket seal may be provided on both the openingportion 12 and thedoor 13 depending on the shape of the gasket seal. - The constitutions described in the embodiments described above may be also freely selected or appropriately changed into other constitutions without departing from the scope of the present invention.
-
- 10 Aircraft
- 11 Skin
- 12 Opening portion
- 13 Door (Closing body)
- 14, 14A Seal retention portion
- 20, 20A, 20B, 20C, 20D Gasket seal
- 12 Seal portion
- 22 Base portion
- 24 Conductive fiber
- 30, 30A Striker (Metallic fitting)
- 31 Edge member (Door frame)
- 32, 32A Plating layer
- 33 Coating layer (Anticorrosion coating)
- 50 Scuff plate (Metallic fitting)
- 60A Door-side bonding strap (Metallic fitting, First bonding strap)
- 60B Airframe opening portion-side bonding strap (Metallic fitting, Second bonding strap)
- 100 Door frame
Claims (19)
1. A gasket seal which is arranged between an opening portion formed in an airframe of an aircraft and a closing body for closing the opening portion, the gasket seal comprising:
a gasket seal body that is made of a rubber material; and
conductive fiber that covers a surface of the gasket seal body.
2. The gasket seal according to claim 1 , wherein the conductive fiber is one of a) synthetic fiber where a metal plating film is formed on a surface, b) metal fiber, and c) polymer fiber including a conductive material.
3. The gasket seal according to claim 1 , wherein the rubber material is silicone rubber.
4. The gasket seal according to claim 1 , wherein the rubber material is conductive rubber into which a conductive filler is mixed.
5. A door of an aircraft using the gasket seal according to claim 1 .
6. A seal structure for an opening portion of an aircraft using the gasket seal according to claim 1 , the seal structure comprising:
the closing body that closes the opening portion;
the gasket seal provided on one of the opening portion and the closing body; and
a metallic fitting that is provided on the other of the opening portion and the closing body, and electrically connected to the gasket seal.
7. A seal structure for an opening portion of an aircraft using the gasket seal according to claim 1 , the seal structure comprising:
the closing body that closes the opening portion;
the gasket seal provided on one of the opening portion and the closing body; and
a striker or a scuff plate that is provided on the other of the opening portion and the closing body, and abutted against the gasket seal when the closing body is closed,
wherein a base material of the striker and the scuff plate is a conductive material.
8. The seal structure for an opening portion of an aircraft according to claim 6 ,
wherein the closing body is a door,
the gasket seal is provided on the door, and
the striker or the scuff plate is provided on a door frame formed at the opening portion.
9. The seal structure for an opening portion of an aircraft according to claim 7 , wherein the striker or the scuff plate includes a plating layer at least on a contact surface with the conductive fiber of the gasket seal.
10. The seal structure for an opening portion of an aircraft according to claim 9 ,
wherein the conductive fiber of the gasket seal is the synthetic fiber where a metal plating film is formed on a surface, and
an anodic index of a metal material constituting the metal plating film is equal to or almost equal to an anodic index of a metal material constituting the plating layer of the striker or the scuff plate.
11. The seal structure for an opening portion of an aircraft according to claim 9 ,
wherein the conductive fiber of the gasket seal is the metal fiber, and
an anodic index of a metal material constituting the metal fiber is equal to or almost equal to an anodic index of a metal material constituting the plating layer of the striker or the scuff plate.
12. The seal structure for an opening portion of an aircraft according to claim 9 , wherein the plating layer of the striker or the scuff plate is a plating layer containing nickel or chrome as a main component.
13. The seal structure for an opening portion of an aircraft according to claim 12 , wherein the plating layer of the striker or the scuff plate is an electroless nickel plating layer or a hard chrome plating layer.
14. The seal structure for an opening portion of an aircraft according to claim 9 , wherein the plating layer of the striker or the scuff plate is a plating layer containing tin as a main component.
15. The seal structure for an opening portion of an aircraft according to claim 9 ,
wherein the plating layer of the striker or the scuff plate is a nickel plating layer, and
the conductive fiber of the gasket seal is obtained by forming a metal plating film containing nickel, copper, silver, gold, or alloy thereof as a main component on a surface of synthetic fiber.
16. The seal structure for an opening portion of an aircraft according to claim 9 ,
wherein the plating layer of the striker or the scuff plate is a chrome plating layer or a tin plating layer, and
the conductive fiber of the gasket seal is made of metal fiber formed of 300 series stainless steel, 400 series stainless steel, or 2000 series aluminum alloy.
17. The seal structure for an opening portion of an aircraft according to claim 9 , wherein a region of the striker other than a region where the plating layer is formed is covered with an anticorrosion coating having insulating properties.
18. A seal structure for an opening portion of an aircraft using the gasket seal according to claim 1 ,
wherein the closing body is a door,
a first bonding strap made of corrosion resistant steel is provided on the door while supporting the gasket seal,
a second bonding strap made of corrosion resistant steel is provided on a door frame formed at the opening portion, and
the first bonding strap is abutted against the second bonding strap when the door is closed.
19. An aircraft having the seal structure according to claim 6 .
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JP2011-205028 | 2011-09-20 | ||
PCT/JP2012/005970 WO2013042362A1 (en) | 2011-09-20 | 2012-09-20 | Gasket seal, aircraft door, seal structure for aircraft opening, and aircraft |
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PCT/JP2012/005970 A-371-Of-International WO2013042362A1 (en) | 2011-09-20 | 2012-09-20 | Gasket seal, aircraft door, seal structure for aircraft opening, and aircraft |
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US15/444,587 Division US9777838B2 (en) | 2011-09-20 | 2017-02-28 | Gasket seal, door of aircraft, seal structure for opening portion of aircraft, and aircraft |
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US15/444,587 Active US9777838B2 (en) | 2011-09-20 | 2017-02-28 | Gasket seal, door of aircraft, seal structure for opening portion of aircraft, and aircraft |
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Also Published As
Publication number | Publication date |
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JPWO2013042362A1 (en) | 2015-03-26 |
US9777838B2 (en) | 2017-10-03 |
US20170167611A1 (en) | 2017-06-15 |
WO2013042362A1 (en) | 2013-03-28 |
JP5734445B2 (en) | 2015-06-17 |
US9617783B2 (en) | 2017-04-11 |
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